CN111033016A - Fuel metering circuit and method for compensating for fuel density variability - Google Patents
Fuel metering circuit and method for compensating for fuel density variability Download PDFInfo
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- CN111033016A CN111033016A CN201880049203.6A CN201880049203A CN111033016A CN 111033016 A CN111033016 A CN 111033016A CN 201880049203 A CN201880049203 A CN 201880049203A CN 111033016 A CN111033016 A CN 111033016A
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- fuel
- metering
- metering device
- volumetric flow
- density
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/232—Fuel valves; Draining valves or systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/263—Control of fuel supply by means of fuel metering valves
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/35—Combustors or associated equipment
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/60—Fluid transfer
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Measuring Volume Flow (AREA)
- Flow Control (AREA)
Abstract
A fuel metering circuit (1) for a turbomachine, comprising: -a metering device (6), -a pump (4), -a control valve (5) configured to return an excess fuel flow delivered to the metering device (6) towards the pump (4) as a function of a fuel pressure difference at terminals of the metering device (6), -a diaphragm (8), and-a volumetric flow meter (9), the diaphragm (8) and the volumetric flow meter (9) being mounted downstream of the control valve (5) in parallel with the metering device (6) to determine the density of the fuel flowing in the metering circuit (1).
Description
Technical Field
The present invention relates to a fuel metering circuit for a turbomachine and to a metering method that can be implemented by such a circuit.
Background
Turbines generally comprise a fuel metering circuit comprising a fuel metering device which delivers a fuel flow rate adapted to the operating speed of the turbine to a combustion chamber of the turbine.
The metering circuit also comprises (in the case of a turbojet engine equipped with an aircraft fuel tank integrated into the aircraft-in contrast to an aircraft architecture equipped with a turbine instead of a turbojet engine and with an integral tank) a pump that draws fuel from the fuel tank of the turbine to deliver it to the metering device, and a regulating valve that enables the excess fuel flow supplied to the metering device to be recirculated towards the pump.
Each operating speed of the turbine imposes a corresponding fuel mass flow, which must be delivered by the metering device. Fig. 1 shows the density of different types of fuel as a function of temperature (each curve numbered 1 to 4 corresponds to a different fuel, and the curve numbered 5 corresponds to one example of engine size). It can be seen in this figure that the density of the fuel can vary significantly, in particular with the type of fuel used (more or less volatile fuel) and the fuel temperature. Currently, the metering device is controlled according to a control law which relates the desired target mass flow to the position of the metering device for defined conditions of temperature and fuel type.
These control laws therefore do not allow for the variability of the fuel density to be taken into account when controlling the metering device, so that the metered mass flow cannot be accurately adapted to the density of the fuel to obtain the target mass flow.
Furthermore, since the flow meter used to know the quantity of fuel delivered by the metering device is a volumetric flow meter, it is not possible to know the mass flow delivered by the metering device accurately, the reactivity of the mass flow meter being insufficient to provide reliable information that is at any time adapted to the engine speed of the turbine.
This results in a significant error of about 12% in the mass flow delivered by the metering device to the fuel combustion chamber.
The proportion of the error in the flow delivered by the metering device, which error is caused by the unknown fuel density, can be calculated by the following equation (a) which represents the delivered flow:
wherein:
wf is the mass flow injected by the metering device, in kg/h
- ρ is the flow density in kg/L
-K is a constant, and
s is the open cross-section of the groove of the metering device in mm2
The effect of density on the injected flow is as follows:
and at 803kg/m3In comparison with the law of average density calculation, the density is 700kg/m3To 900kg/m3This variation results in an error in the injected mass flow between-6.4 and 6.1%.
However, this error affects the size of the turbine.
In particular, significant changes in the rotational speed of the turbine (e.g., from a high speed range to an idle rotational speed, and from an idle rotational speed to a high speed range) result in sudden changes in the flow delivered to the combustor. The variation occurs in a time shorter than the variation time of the turbine rotational speed. Therefore, operating tolerances (known as surge and shutdown margins) must be defined so that the turbine can continue to operate despite the delivered flow being different from the appropriate demand required for operation and being adapted to the current rotational speed of the turbine, these tolerances being achieved by margins in selected parameters of the turbine.
Due to the large error in the flow delivered by the metering device, the tolerances and the margins for the selected parameters of the turbine must be larger.
Some solutions have been proposed, including the use of a temperature sensor combined with a calculator that corrects the control of the metering device according to a compensation law established on the basis of the temperature or density of the fuel.
However, this solution allows to correct only a part of the temperature-related deviations by further increasing other sources of uncertainty related to the drafting of the law.
Disclosure of Invention
The present invention aims to overcome the drawbacks of the prior art by proposing a fuel metering system having an increased accuracy with respect to the metered flow rate compared to the prior art.
To this end, the invention proposes a fuel metering circuit for a turbomachine, comprising:
-a metering device for metering the liquid in the tank,
a pump configured to circulate a fuel flow towards the metering device,
a regulating valve configured to return the excess fuel flow delivered to the metering device towards the pump as a function of the fuel pressure difference at the metering device terminals,
-a membrane, and
-a volumetric flow meter configured to determine the volumetric flow rate of the fuel through the membrane.
The diaphragm and the volumetric flowmeter are mounted in the bypass pipe in parallel with the metering device, downstream of the regulating valve, in order to determine the density of the fuel circulating in the metering circuit.
Some preferred but non-limiting features of the metering circuit described above are as follows, which may be employed alone or in combination:
the volumetric flow meter is mounted upstream or downstream of the diaphragm.
The metering circuit further comprises an electronic card configured to receive information from the volumetric flowmeter about the volumetric flow rate of the fuel and to adjust the monitoring setpoint of the metering device by taking into account the fuel density thus determined.
The pump comprises a volumetric pump.
According to a second aspect, the invention also proposes a turbomachine comprising such a metering circuit.
According to a third aspect, the invention proposes a fuel metering method implemented in a fuel metering circuit, characterized in that it comprises the following steps:
-determining a pressure difference at a terminal of the metering device,
-measuring the volumetric flow of fuel by using a volumetric flow meter,
-calculating the fuel density from the pressure difference, the volume flow and a constant related to the membrane.
Some preferred but non-limiting features of the above described metering method are as follows, which features may be used alone or in combination:
-the method further comprises the steps of: during this step, the flow meter transmits information relating to the volumetric flow rate of the fuel to the electronic card, and the electronic card adjusts the monitoring set point of the metering device by taking into account the fuel density.
-monitoring the fuel flow by recirculating a variable fuel flow towards the pump by means of a regulating valve.
Drawings
Other features, objects and advantages of the invention will become apparent upon reading the following detailed description and upon reference to the drawings, given by way of non-limiting example, and in which:
the described figure 1 shows the variation of the density of various fuels with temperature.
Figure 2 schematically shows a metering circuit according to an embodiment of the invention.
Fig. 3 is a flow chart illustrating the steps of an exemplary embodiment of a metering method according to the present invention.
Detailed Description
Fig. 2 shows a flow metering circuit 1 for a turbomachine comprising at least one combustion chamber 2 and one fuel tank 3.
The fuel metering circuit 1 comprises a volumetric pump 4, a metering device 6 and a metering device supply line (referred to as high-pressure supply line) which connects the outlet of the volumetric pump 4 to the inlet of the metering device 6. The metering device 6 is adapted to deliver a target mass flow to the combustion chamber 2 from an initial flow delivered to the combustion chamber by the volumetric pump 4 via a high-voltage line.
The metering device 6 comprises a surface of variable size, called the metering device opening surface, which enables the liquid to flow. The flow delivered by the metering device 6 is therefore dependent in particular on the opening surface.
The opening surface of the metering device 6 is variable under the drive of a servo valve which controls the movement of a movable metering member to progressively block the metering orifice or slot. The position sensor enables the position of the movable part to be known. The position sensor is typically a LDVT (linear variable differential transformer) sensor.
There are different types of metering devices 6, for example metering devices with a conventional metering tank described in document US 7526911 or with an index tank described in documents EP 1231368 and FR 2825120. In the case of an exponential slot, the opening surface increases exponentially with the movement of the movable part, which enables better precision at low flow rates.
The metering circuit may further comprise a Shut-off Valve 10 or HPSOV (High Pressure Shut-off Valve), which is configured to allow or prevent fuel injection into the combustion chamber.
Alternatively, the metering circuit 1 may comprise an electronic card 11 to monitor the metering of the fuel. To this end, the electronic card can communicate with the metering device 6, for example, in two directions: the electronic card can send position setting points to the metering device 6 and recover data on the metering device.
The electronic card 11 can also be connected to a monitoring unit external to the device. The monitoring unit is typically an electronic Control unit ECU (Engine Control unit) of a FADEC (english acronym of full authority Digital Engine Control, i.e. full authority Digital Control system), which monitors the variable geometry of the aircraft (actuators, metering devices, etc.). The monitoring unit may be located within the perimeter of the aircraft and therefore cannot be used only for conditioning the fuel. Instead, the electronic card 11 is preferably dedicated only to the metering and auxiliary functions of the fuel. As a variant, in addition to the main monitoring device, there may be an additional monitoring device, which may be dedicated in particular to metering. The connection between the monitoring unit and the electronic card 11 is usually realized by a connection harness.
Only the electronic card 11 of the metering circuit 1 is connected (by a single harness) to the aircraft monitoring unit and then redistributed within the metering circuit 1 by the electronic card 11. Thus, the metering circuit 1 comprises: a single inlet from the monitoring unit to the electronic card 11, which divides it into a plurality of outlets, i.e. in particular the metering device 6.
The fuel metering circuit 1 further comprises a regulating valve 5, which regulating valve 5 is adapted to regulating the flow delivered to the metering device 6. In particular, the regulating valve 5 is adapted to return the excess fuel flow reaching the metering device 6 at the inlet of the volumetric pump 4 according to the pressure difference at the terminals of the metering device 6. The regulating valve 5 also serves to keep the fuel pressure difference Δ P between upstream and downstream of the metering device 6 constant.
Typically, the regulating valve 5 comprises a movable flap which acts against the action of a loaded spring on the predetermined value of the pressure difference Δ P to be maintained. The baffle is generally perforated in order to discharge the fuel on the conduit leading to the recirculation circuit according to the equilibrium position of the baffle against the action of the spring.
One example of a regulating valve 5 that can be used here is described in document FR 1655944 filed by the applicant on day 27, 6/2016.
In order to be able to accurately set small openings, the metering circuit 1 further comprises a bypass 7, which bypass 7 is arranged in parallel with the metering device 6 and comprises a minimum flow diaphragm 8 and a volumetric flow meter 9.
The diaphragm 8 has a fixed section SdThe fixed section is set during a preliminary test performed on the bench. In general, the septum may include an orifice having a fixed size and shape.
A pressure difference is applied at the terminals of the diaphragm 8, which pressure difference is regulated and defined by the regulating valve 5, as described above. Since the diaphragm is mounted in parallel with the metering device 6 in the bypass circuit 7, this pressure difference Δ P is equal to the pressure difference Δ P at the terminals of the metering device 6.
The pressure difference Δ P can be measured in particular by means of a differential sensor.
Further, the head loss due to passage through the diaphragm 8 is determined by the following formula (B):
wherein
ρ is the density of the fuel and is,
ξ, is the head loss coefficient of the diaphragm 8, which is constant,
q is a cross-section SdThe volume flow of the diaphragm 8.
However, the pressures upstream and downstream of the diaphragm 8 are known and defined by the regulating valve 5. Differential sensors may also be used to measure the pressure. The cross section of the diaphragm 8 is determined beforehand by tests carried out on a bench. The volume flow is measured using a volume flow meter 9 arranged in series with the diaphragm 8 (upstream or downstream of the diaphragm 8 in the bypass pipe 7). Finally, the head loss coefficient of the diaphragm 8 is constant: thus, the ratio
Is also a constant.
From equation (B) it is deduced that the volumetric flow Q varies only with the fuel density within the measurement error.
The diaphragm 8 and the volumetric flowmeter 9, which are arranged in series in the bypass pipe, thus form an inline densitometer which enables the overall accuracy of the metering circuit 1 to be improved.
When the metering circuit 1 comprises, where appropriate, an electronic card 11, the measurement results measured by the flowmeter 9 are transmitted to the electronic card 11, so that the latter derives the fuel density from the measurement results. The electronic card 11 can then adjust the monitoring set point of the metering device 6 by taking into account the bulk density of the fuel.
As a variant, in the absence of the electronic card 11 in the metering circuit 1, the measurement result measured by the flow meter 9 is transmitted directly to the control unit of the metering device 6.
In order to estimate the metering accuracy achieved by the diaphragm 8 and the additional flow meter 9, the calibration accuracy previously achieved during the test on the test bench and the measurement inaccuracies in normal operation have to be taken into account.
The accuracy of the volumetric flow meter 9 is about +/-0.8% of the measurement. This possible deviation takes into account the entire temperature range, depending on the measured flow. However, in the opposite case, the temperature in the bypass 7, including the diaphragm 8 and the flow meter 9, can be measured and the correction can be made to the flow read, the turbine flow meter being sensitive to the viscosity of the fluid.
Furthermore, during preliminary tests on the bench, the electronics are calibrated more finely than the onboard electronics. Thus, the uncertainty of the characterization (typically +/-0.5% of the measurement) is lower.
In the following, from a conservative point of view, it will be considered that the measurement accuracy in calibration and operation is the same within +/-0.8% of the entire measured temperature.
Likewise, the accuracy of the differential pressure sensor is +/-0.8% of full scale.
For the balance table, a 5 bar range will be considered, i.e. an accuracy of about +/-1% for a measurement of 4 bar (the conventional value of regulating the pressure difference).
Consider the following equation, which defines the volume flow of an injection:
wherein:
q is the flow rate measured using the volumetric flow meter 9 and is expressed in L/h
Rho is the fuel density in kg/L
S is the fuel passage section coupled to the opening of the metering device 6
A is the opening in mm of the measuring groove of the measuring device 6
The effect of pressure and volumetric flow on the measured value of fuel density ρ is determined by:
namely:
and
all of these measurement errors are random. Thus the density error ερWill be equal to
Thus, the density obtained through the diaphragm 8 and the volumetric flowmeter 9
The calibrated flow error is
By pressure differencesThe calibrated flow error will be
It is to be noted that in the absence of regulation, the density variation causes a variation of the flow rate from-6.4% to + 6.1%, whereas in the case of regulation, in particular when the metering circuit 1 comprises an electronic card 11, the flow rate variation will be in the range of about +/-1.6%. Without the electronic card 11, the flow variation may be between-3% and + 3%.
Then, the fuel metering using such a fuel metering circuit 1 comprises the steps of:
determining S1 the pressure difference at the terminals of the metering device 6,
measuring S2 the fuel volumetric flow rate using the volumetric flow meter 9,
-calculating S3 the fuel density from the pressure difference, the volume flow and a constant related to the diaphragm 8,
determining information relating to the volumetric flow rate of the fuel and transmitting S4 this information to the electronic card 11, so that the electronic card 11 adjusts the monitoring set point of the metering device 6 by taking into account the fuel density.
It should be noted that the fuel flow rate S4 is monitored by recirculating a variable fuel flow rate towards the pump 4 by means of the regulating valve 5.
Claims (8)
1. A fuel metering circuit (1) for a turbomachine, comprising:
-a metering device (6),
-a pump (4) configured to circulate a fuel flow towards the metering device (6),
-a regulating valve (5) configured to return the excess fuel flow delivered to the metering device (6) towards the pump (4) as a function of the fuel pressure difference at the terminals of the metering device (6),
-a membrane (8), and
-a volumetric flow meter (9) configured to determine a volumetric flow rate of fuel through the membrane (9),
the metering circuit (1) is characterized in that the diaphragm (8) and the volumetric flowmeter (9) are mounted in the bypass pipe (7) in parallel with the metering device (6) and downstream of the regulating valve (5) to determine the density of the fuel circulating in the metering circuit (1).
2. The metering circuit (1) of claim 1, wherein the volumetric flow meter (9) is mounted upstream or downstream of the diaphragm (8).
3. The metering circuit (1) according to claim 1 or 2, further comprising an electronic card (11) configured to receive information from the volumetric flow meter (9) about the volumetric flow rate of the fuel and to adjust a monitoring setpoint of a metering device (6) by taking into account the fuel density thus determined.
4. The metering circuit (1) of any of claims 1 to 3, wherein the pump (4) comprises a positive displacement pump (4).
5. A turbomachine comprising a fuel metering circuit (1) according to any one of claims 1 to 4.
6. A fuel metering method (S) implemented in a fuel metering circuit (1) according to any one of claims 1 to 4, characterized in that it comprises the steps of:
-determining (S1) a pressure difference at a terminal of the metering device (6),
-measuring (S2) the volumetric flow of the fuel using the volumetric flow meter (9),
-calculating (S3) the fuel density from the pressure difference, the volume flow and a constant related to the diaphragm (8).
7. The metering method (S) according to claim 6, further comprising a step (S4) during which the flowmeter transmits information relating to the volumetric flow rate of the fuel to an electronic card (11), and the electronic card (11) adjusts the monitoring set point of the metering device (6) by taking into account the fuel density.
8. The metering method (S) according to claim 6 or 7, wherein the fuel flow is monitored (S4) by recirculating a variable fuel flow towards the pump (4) by means of the regulating valve (5).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR1756706 | 2017-07-13 | ||
| FR1756706A FR3069021B1 (en) | 2017-07-13 | 2017-07-13 | FUEL DOSING SYSTEM AND METHOD COMPRISING VARIABILITY OF FUEL DENSITY |
| PCT/FR2018/051778 WO2019012238A1 (en) | 2017-07-13 | 2018-07-13 | Fuel metering circuit and method with compensation for fuel-density variability |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111033016A true CN111033016A (en) | 2020-04-17 |
| CN111033016B CN111033016B (en) | 2022-03-29 |
Family
ID=59811623
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201880049203.6A Active CN111033016B (en) | 2017-07-13 | 2018-07-13 | Fuel metering circuit and method for compensating for fuel density variability |
Country Status (8)
| Country | Link |
|---|---|
| US (1) | US11365692B2 (en) |
| EP (1) | EP3652425B1 (en) |
| CN (1) | CN111033016B (en) |
| BR (1) | BR112020000625B1 (en) |
| CA (1) | CA3069609A1 (en) |
| FR (1) | FR3069021B1 (en) |
| RU (1) | RU2763240C2 (en) |
| WO (1) | WO2019012238A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115788684A (en) * | 2022-11-10 | 2023-03-14 | 中国航发北京航科发动机控制系统科技有限公司 | Fuel oil metering device with temperature compensation function and metering method |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3094086B1 (en) | 2019-03-19 | 2021-03-19 | Safran Aircraft Engines | Method for monitoring the operating state of a hydromechanical unit |
| FR3098255B1 (en) | 2019-07-03 | 2021-06-04 | Safran Aircraft Engines | Determination of fuel density for metering fuel in a fuel supply system of an aircraft engine |
| US11635031B2 (en) * | 2019-11-08 | 2023-04-25 | Hamilton Sundstrand Corporation | Simultaneously pumping and measuring density of aircraft fuel |
| US11629717B2 (en) * | 2019-11-08 | 2023-04-18 | Hamilton Sundstrand Corporation | Simultaneously pumping and measuring density of aircraft fuel |
| FR3110195B1 (en) * | 2020-05-18 | 2022-08-19 | Safran Aerosystems | Aircraft comprising in its fuel tank a chamber equipped with a sensor |
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| US4809499A (en) * | 1987-03-20 | 1989-03-07 | United Technologies Corporation | Densimeter |
| CN1032840A (en) * | 1987-10-22 | 1989-05-10 | 联合工艺公司 | The temperature correction of metering valve |
| US20120042657A1 (en) * | 2009-04-29 | 2012-02-23 | Snecma | method and device for feeding a turbomachine combustion chamber with a regulated flow of fuel |
| US20160123860A1 (en) * | 2014-10-31 | 2016-05-05 | Simmonds Precision Products, Inc. | Fuel density determination |
| US20170038238A1 (en) * | 2015-08-05 | 2017-02-09 | The Boeing Company | Methods and Systems for Direct Fuel Quantity Measurement |
| US20170101935A1 (en) * | 2014-06-05 | 2017-04-13 | Safran Aircraft Engines | System for supplying a turbine engine with fluid having a low pressure pumping assembly comprising two pumps in parallel |
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|---|---|---|---|---|
| US2809492A (en) * | 1952-12-23 | 1957-10-15 | Simmonds Aerocessories Inc | Apparatus for measuring and/or controlling fuel/air ratio of gas turbines without direct gravimetric fuel metering |
| FR2818690B1 (en) | 2000-12-22 | 2003-03-21 | Snecma Moteurs | TWO-LEVEL PRESSURIZATION VALVE CONTROLLED BY A FUEL DISPENSER |
| FR2825120B1 (en) * | 2001-05-25 | 2003-12-12 | Snecma Moteurs | DOSER WITH 2 INTEGRATED OUTPUTS |
| US6655151B2 (en) * | 2001-09-07 | 2003-12-02 | Honeywell International, Inc. | Method for controlling fuel flow to a gas turbine engine |
| US7526911B2 (en) | 2006-02-03 | 2009-05-05 | Rolls-Royce Corporation | Gas turbine engine fuel system with fuel metering valve |
| US7784487B2 (en) * | 2007-10-24 | 2010-08-31 | Honeywell International Inc. | Fuel metering valve assembly including thermal compensation mechanism |
| US20120167594A1 (en) * | 2011-01-05 | 2012-07-05 | Hamilton Sundstrand Corporation | Bypass Monitor for Fuel Supply System |
-
2017
- 2017-07-13 FR FR1756706A patent/FR3069021B1/en not_active Expired - Fee Related
-
2018
- 2018-07-13 CN CN201880049203.6A patent/CN111033016B/en active Active
- 2018-07-13 BR BR112020000625-4A patent/BR112020000625B1/en active IP Right Grant
- 2018-07-13 US US16/630,705 patent/US11365692B2/en active Active
- 2018-07-13 CA CA3069609A patent/CA3069609A1/en active Pending
- 2018-07-13 RU RU2020106377A patent/RU2763240C2/en active
- 2018-07-13 WO PCT/FR2018/051778 patent/WO2019012238A1/en unknown
- 2018-07-13 EP EP18758920.5A patent/EP3652425B1/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4809499A (en) * | 1987-03-20 | 1989-03-07 | United Technologies Corporation | Densimeter |
| CN1032840A (en) * | 1987-10-22 | 1989-05-10 | 联合工艺公司 | The temperature correction of metering valve |
| US20120042657A1 (en) * | 2009-04-29 | 2012-02-23 | Snecma | method and device for feeding a turbomachine combustion chamber with a regulated flow of fuel |
| US20170101935A1 (en) * | 2014-06-05 | 2017-04-13 | Safran Aircraft Engines | System for supplying a turbine engine with fluid having a low pressure pumping assembly comprising two pumps in parallel |
| US20160123860A1 (en) * | 2014-10-31 | 2016-05-05 | Simmonds Precision Products, Inc. | Fuel density determination |
| US20170038238A1 (en) * | 2015-08-05 | 2017-02-09 | The Boeing Company | Methods and Systems for Direct Fuel Quantity Measurement |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115788684A (en) * | 2022-11-10 | 2023-03-14 | 中国航发北京航科发动机控制系统科技有限公司 | Fuel oil metering device with temperature compensation function and metering method |
Also Published As
| Publication number | Publication date |
|---|---|
| RU2020106377A (en) | 2021-08-13 |
| EP3652425A1 (en) | 2020-05-20 |
| BR112020000625B1 (en) | 2023-10-03 |
| WO2019012238A1 (en) | 2019-01-17 |
| BR112020000625A2 (en) | 2020-07-14 |
| CN111033016B (en) | 2022-03-29 |
| US20210087980A1 (en) | 2021-03-25 |
| US11365692B2 (en) | 2022-06-21 |
| EP3652425B1 (en) | 2021-05-26 |
| RU2020106377A3 (en) | 2021-11-12 |
| FR3069021B1 (en) | 2019-07-26 |
| FR3069021A1 (en) | 2019-01-18 |
| RU2763240C2 (en) | 2021-12-28 |
| CA3069609A1 (en) | 2019-01-17 |
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